Mr. Toshimichi Ogisu Profile

Toshimichi Ogisu

Manager at Fuji Heavy Industries Ltd

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Author

Publications (11)

Proceedings Article | 8 April 2008 Paper

Demonstration of detectability of SHM system with FBG/PZT hybrid system in composite wing box structure

Hideki Soejima, Toshimichi Ogisu, Hiroshi Yoneda, Yoji Okabe, Nobuo Takeda, Yasuhiro Koshioka

Proceedings Volume 6932, 69322E (2008) https://doi.org/10.1117/12.776078

KEYWORDS: Sensors, Fiber Bragg gratings, Ferroelectric materials, Structural health monitoring, Composites, Connectors, Aircraft structures, Inspection, Actuators, Skin

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Proceedings Article | 19 April 2007 Paper

Nondestructive detection of delamination and debonding of CFRP by a laser-based ultrasonic visualization method

J. Takatsubo, S. Yashiro, H. Tsuda, N. Toyama, J.R. Lee, T. Ogisu

Proceedings Volume 6531, 653108 (2007) https://doi.org/10.1117/12.714449

KEYWORDS: Ultrasonics, Wave propagation, Visualization, Inspection, Nondestructive evaluation, Sensors, Skin, Signal detection, Ferroelectric materials, Pulsed laser operation

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Proceedings Article | 11 April 2007 Paper

Impact monitoring of the aircraft composite structure using FBG sensor/PZT actuator hybrid sensor system

Noritsugu Nakamura, Toshimichi Ogisu, Hiroshi Yoneda, Yoji Okabe, Nobuo Takeda, Tateo Sakurai

Proceedings Volume 6527, 65270B (2007) https://doi.org/10.1117/12.715584

KEYWORDS: Fiber Bragg gratings, Sensors, Composites, Actuators, Aircraft structures, Ferroelectric materials, Structural health monitoring, Optical filters, Optical fibers, Reflection

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Proceedings Article | 30 March 2006 Paper

Damage growth monitoring for a bonding layer of the aircraft bonding structure

Toshimichi Ogisu, Masakazu Shimanuki, Hiroshi Yoneda, Yoji Okabe, Junichiro Kuwahara, Nobuo Takeda, Tateo Sakurai

Proceedings Volume 6171, 61710C (2006) https://doi.org/10.1117/12.658555

KEYWORDS: Fiber Bragg gratings, Sensors, Composites, Ferroelectric materials, Optical fibers, Fiber optics sensors, Structural health monitoring, Interfaces, Wave propagation, Optical components

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Proceedings Article | 16 March 2006 Paper

Evaluation of debonding progress in composite bonded structures by ultrasonic wave sensing with fiber Bragg grating sensors

Yoji Okabe, Junichiro Kuwahara, Nobuo Takeda, Toshimichi Ogisu, Seiji Kojima, Shinji Komatsuzaki

Proceedings Volume 6179, 61790G (2006) https://doi.org/10.1117/12.657510

KEYWORDS: Fiber Bragg gratings, Sensors, Ultrasonics, Adhesives, Wave propagation, Wavelet transforms, Skin, Actuators, Wavelets, Optical filters

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Proceedings Article | 16 May 2005 Paper

Damage growth detection of composite laminate using embedded FBG sensor/PZT actuator hybrid system

Toshimichi Ogisu, Masakazu Shimanuki, Satoshi Kiyoshima, Yoji Okabe, Nobuo Takeda

Proceedings Volume 5758, (2005) https://doi.org/10.1117/12.598085

KEYWORDS: Fiber Bragg gratings, Sensors, Composites, Actuators, Fiber optics sensors, Ferroelectric materials, Structural health monitoring, Aircraft structures, Interfaces, Optical fibers

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This paper presents a part of the study conducted for developing a damage diagnostic system for an advanced composite material that can be utilized in next-generation aircraft structure. The authors have been working on a detection of elastic wave which can be launched from the PZT actuators, using small- and normal-diameter FBG optical fiber sensors that are bonded to the surface of the CFRP laminate under different conditions. Based on the results, it was verified that it is possible to achieve a high-accuracy detection of elastic wave by using FBG sensors bonded to the surface of the CFRP laminate. It was also verified that the damages generated on the inside of the composite material may be detected by the waveform analysis of the received elastic wave. In this study, the authors succeeded in the embedment of small-diameter FBG optical fiber sensors into the bonding surface of the double-lap type coupon specimen, which simulates the bonding structure of the CFRP composite structure. In this study, we also clarified several issues pertaining to the conditions, methods, and techniques involved in fiber embedding. An optical loss was observed during the embedment process, which may result in the loss of both accuracy and reliability. Based on these observations, the authors developed embedding techniques for optical fiber sensors that can reduce this optical loss. Additionally, the possibility of detecting an elastic wave, which was launched from the PZT actuators bonded to the surface of the coupon and directed to the host material, was verified using double-lap type coupon specimen having embedded small-diameter FBG optical fiber sensors at the bonding surface. Therefore, this specimen has provided an artificial defect that simulates the delamination generated at the bonding interface. Based on the measurements of the elastic wave, it was verified that the change in the elastic wave depends on the damage length, which is caused by the artificial defect. Moreover, based on the analysis of the received elastic wave, the possibility of damage detection was confirmed. The successful development of this damage monitoring system would ease the implementation of structural health monitoring system in aircraft structures in the near future.

Proceedings Article | 29 July 2004 Paper

Development of damage monitoring system for aircraft structure using a PZT actuator/FBG sensor hybrid system

Toshimichi Ogisu, Masakazu Shimanuki, Satoshi Kiyoshima, Yoji Okabe, Nobuo Takeda

Proceedings Volume 5388, (2004) https://doi.org/10.1117/12.539727

KEYWORDS: Sensors, Fiber Bragg gratings, Composites, Ferroelectric materials, Aircraft structures, Actuators, Fiber optics sensors, Electronic filtering, Aluminum, Reliability

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This paper presents a part of the research results on a damage monitoring system using PZT actuators/FBG sensors for advanced composite material structures of new-generation aircrafts. To achieve weight reduction of the aircraft structure, these advanced composite materials have gradually been employed for the primary structure. It is expected that when these materials are extensively employed, an efficient bonded structure such as a hat-shaped stringer will be utilized for the aircraft structure. However, these bonded structures have critical problems such as debonding and delamination at the interfaces of the laminate. Further, a single-step molding process of the structure elements is necessary in order to ensure low cost and thus affordability. However, this low-cost process results in an increase in the non-destructive inspection (NDI) cost. Therefore, an innovative damage monitoring system is required for structural health management. In the present study, the authors have developed a hybrid sensor system that can detect the elastic waves launched from the piezo transducer (PZT) actuator using a high-speed and high-accuracy fiber Bragg grating (FBG) sensor to resolve the issues mentioned above. In this study, the conceptual design of an aircraft that can employ this damage monitoring system was carried out. Subsequently, the application area was selected based on cases of certain kinds of damage. Further, the validity of the damage monitoring system for the verification of the structural integrity of the aircraft was discussed. Next, in order to verify the elastic wave detectability of the FBG sensor, it was confirmed that an elastic wave of 300 kHz is detectable at a distance of 5 cm between the PZT actuator and FBG sensor using an aluminum sheet and CFRP cross-ply laminate and also by considering the relationship between sensor length and sensitivity. Through the present research results, the possibility of applying the damage monitoring system to the composite material bonding structure in an aircraft is presented.

Proceedings Article | 14 August 2003 Paper

Damage suppression system using embedded SMA (shape memory alloy) foils in CFRP laminate structures

Toshimichi Ogisu, Masakazu Shimanuki, Satoshi Kiyoshima, Junji Takaki, Nobuo Takeda

Proceedings Volume 5054, (2003) https://doi.org/10.1117/12.483882

KEYWORDS: Shape memory alloys, Smart materials, Actuators, Aircraft structures, Embedded systems, Manufacturing, Aluminum, Structural health monitoring, Skin, Radon

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Proceedings Article | 9 July 2002 Paper

Application study on aircraft structures of CFRP laminates with embedded SMA foils

Toshimichi Ogisu, Masato Nomura, Norio Ando, Junji Takaki, Nobuo Takeda

Proceedings Volume 4698, (2002) https://doi.org/10.1117/12.475085

KEYWORDS: Shape memory alloys, Smart materials, Chemical elements, Manufacturing, Composites, Aircraft structures, Resistance, Adhesives, Actuators, Smart structures

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Proceedings Article | 11 July 2001 Paper

Development of damage suppression system using embedded SMA foil in CFRP laminates

Toshimichi Ogisu, Masato Nomura, Norio Ando, Junji Takaki, Masakazu Kobayashi, Tomonaga Okabe, Nobuo Takeda

Proceedings Volume 4333, (2001) https://doi.org/10.1117/12.432778

KEYWORDS: Shape memory alloys, Oxides, Adhesives, Resistance, Composites, Metals, Embedded systems, Ions, Actuators, Smart materials

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Proceedings Article | 12 June 2000 Paper

Development of damage suppression system using embedded SMA foil sensor and actuator

Toshimichi Ogisu, Masato Nomura, Norio Ando, Junji Takaki, Dong Song, Nobuo Takeda

Proceedings Volume 3991, (2000) https://doi.org/10.1117/12.388147

KEYWORDS: Shape memory alloys, Resistance, Adhesives, Oxides, Actuators, Sensors, Ions, Plating, Coating, Embedded systems

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Showing 5 of 11 publications

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